Combustion turbine



June 28, 1949. I 5, c gso 2,474,404

COMBUSTION TURBINE Filed 060. 6, 1945 2 Sheets-Sheet 1 FIGA.

SA NFORD E R/cHES o/v INVENTOR ATTO R N EY June 28, 1949. s. E. RICHESONcounusuou TURBINE 2 Sheets-Sheet mad Dec. e; 1945 SA NFOFD E R/CI/Es o/vINVENTOR ad f.

ATTO R N EY at which theya relatively high 3 Fig. 3 is the line 3-3 ofFig. 1;

- compressor.

' be provided with Patented June'28, 1949 I v 9 Claims.

My invention relates combustion turbines and has particularreference'to' turbines operated by hot gaseous products of combustion,the turbine operating a compressor for supplying air to a combustionchamber;

My invention has for its object to provide a (01. sou combustion turbineof the general character indicated above in which the compressor is soconstructed as to reduce frictional losses to a point will practicallydisappear.

Another object of myinvention is to provide specially constructed bladeswhich will withstand possible to maintain high operating temperatures inthe turbine for increasing: its power output and efficiency. The useofhigh temperatures tercoolers inthe compressor, thereby also reducinglosses and increasing efiiciency. Y

The foregoing and other objects and features and advantages of myinvention are more fully explained in the accompanying specification andpose is delivered by a pump Mi operated by the drawing in which:

Fig. 1 is a'sectional bine;

Fig. 2 a detail sectional view of the blades;-

Fig. 4 is a sectional detail view oi the may turbine comprises a tubularMy combustion i having gradually increasing casing or. statorelevational view of my turtemperature thereby making it makes it alsopossible to'eliminate the use .of in-' a; sectional view of the sametaken on .vaporsi'rom the rotor chamber 18. F01: compressing the outsideair, large vanes 30 are provided extending from the-outside of the frontend plates it of the rotor and enclosed by'an inner portion ii of thecasing 28; Vapors from the rotor chamber-l9 are exhausted through ducts82 connected with a disc-shaped hollow impeller 33 having a narrowannular nozzle 34 opening into an annular Venturi restriction 35 openinginto the casing 28. The impeller is provided with curved blades 36 asshown more clearly in Fig. 4, and stationary blades 31 are providedin-the Venturi 34, curved in the opposite direction, the blades of theimpeller act as turbine blades for adding a rotary movement to the'shaft8.

" higher operating temperature, the boiling point of mercury being .614F. Mercury for this purpipe 48 into a cooling jacket 48 surrounding thestator. The vapors pass through the Jacket, being guided by spirallyarranged baffles 48 which cause the. vapors to make several revolutionsdiameters from the rear or intake end (at the left also of afrusto-conical shape. The rotor is closed at the ends by end plates i1,i8 mounted on the shaft 8 and sealing the space 18' in the rotor.

Hot burning gases are supplied to the turbine blades from a combustorflsupported on a bracker 25 in communication with the intake opening ofthe turbine. Fuel, liquid or gaseous. is supplied to the combustor by anozzle 26 which may.

operated by a conventional governor. Compressed air is delivered to thecombustor by a pipe in Fig. 1) to the front'or exhaust end (at the taryblades l5 mounted on atubular rotor l8,

around the stator before theyemerge through a pipe 58. The outer shellof the stator is made of 'steel or other alloy which is not affected bymercury such as an alloy of lead, sodium, copper-and iron. The blades llmade of heat resisting alloy, 'and to facilitate the conduction of heatfrom the blades, 9. layer of a good heat conducting metal 5! isprovided, such as silver, with silver'plugs 82 inside the blades ll(Fig. 2)..

The pipe 58 is connected to a nozzle 55 through which the mercury vaporsare directed into the hollow shaft 6 through a Venturi restriction 8,8for increasing their velocity and forming a seal for the vapors in therotor'. The velocity is further" increased by causing the vapors to passthrough radial tubes 51 extending to' the rotor,

' et 23 attached to the rear plate 2 and having an exhaust pipe 24connected with an annular heata conventional throttle valve blades l5which are made hollow inside to facili-' tate their cooling by thevapors. The rotor is also lined inside with a mercuryresisting metal oralloy,-with. a lining 58 of silver or other heat conducting materialbetween the inner lining and the refractory metal of the blades (Fig.2). The opening of the nozzle 68 is controlled by an inner nozzlernovably supported in the rearof the enter nozzle 55 and'moved by ascrew 6| controlled by a suitable conventional pressure responsivedevice 62 for maintaining a desired pressure at the nozzle. The innernozzle 68 is connected by a pipe-68 with the pump 40 and delivers liquidmercury or other liquid into the nozzle 55. A thermocouple 53 is placedin the nozzle 55 and is connected with a, thermostat control valve 59 inthe pipe 84 for regulating the temperature to regulate the flow ofmercury. The liquid breaks up into droplets and boosts pressure andprovides a frictionless seal, delivering a mixture of mercury vapors andliquid mercury into the hollow shaft 6 from which the mixture isprojected by centrifugal force against the inner wall of. the rotor andthe hollow spaces in the blades. 7

Presence of mercury vapors in the cooling medium makes it possible tomaintain the turbine on a high efilciency level by raising the operatingtemperatures of the blades. vaporized in the coil 45 by the exhaustheat, is delivered at 700-800 F. into the spiral jacket 48 around thestator, cooling the stationary blades. The heated vapors are theninjected into the hollow shaft 6 together with the mercury droplets,which are vaporized, reducing the temperature of the mixture to about1000 F. A certain amount of the outside air is admitted through aclearance between a disc 65 on the nozzle 55 and a movable disc66'slidably supported on the'shaft 6 and operated by a centrifugalgovernor 6'! which closes the clearance between the discs 65 and 66.when the shaft is not rotating, thereby preventing loss of the vaporswhen the turbine is not operating. The amount of the air admittedthrough this clearance during rotation of the shaft can be regulated formaintaining a desired temperature of the vapors in the nozzle 55.

The vapors are elected. at a high speed from. the radial pipes propelledby the centrifugal force of the rotor which may make as much as 7000 R.P. M; Liquid mercury is evaporated by the heat of'the blades, and thesuperheatedl, vapors pass through the ducts 32 and are discharged athigh velocity through the annular nozzle 34 into the collector 28 fromwhich they are forced into pipes 10 connected with an annular condenserll surrounding the stator. .The condenser is provided with a pluralityof pockets 12 for the condensed mercury arranged at different points ofthe periphery so that the mercury can be collected in any position ofthe turbine as, for instance, when it is used on an airplane. Thepockets are connected by pipes 13 with the intake of the pump 48. Valves14 are provided in the pipes 13 operated by magnets .15 forclosing thevalves when there is no mercury in'the pocket.

The mercury will be readily condensed since its temperature will bereduced to about 500 F.

Thus, the mercury,

tures, higher operating temperature can be reached even with the samematerials as are now in use, and thus greatly increasing the overallefllciency.

Condensing temperature can be regulated by louvres 80 in an air Jacket8| around the turbine. the louvres being operated'by a thermostaticcontrol device 82 of a conventional type. The jacket 8 I has a commoninner annular wall 83.

If water is used instead of mercury, then the condenser must be keptbelow 212 F. If desired, steam can be admitted into the combustionchamber, increasing the overall efllciency, but a.

' constant supply of water must be then available.

Such a system can be used.to advantage on locomotives, for instance.

The use of mercury in my system has an important advantage in that iteliminates the use of a cooling system for the compressed air, andgreatly increases the efllciency of the turbine,

which depends on the temperature of the air be-.

fore expansion in the combustor. The elimination of the cooling systemreduces the weight of the craft.

power plant thus rendering itpractical for air- The exhaust gasesemerging through exhaust pipes, 85 can be directed to the rear of theaircraft, adding to the propelling power on the rocket principle.

Because of, the large massof the mercury vapors, their passage throughtubes 51 increases the pressure virtually without friction'or loss ofpower in any substantial degree. The pressure is still further increasedby the centrifugal compressor-nozzle 34, whose peripheral speed will bevery great becauseof its large radius.-

'As an added means to prevent the loss of vapors, a closing'disc 86 isprovided at the front sliding on,an extension 81 of the shaft 6 and heldnormally in a closing position against a flange 88 on the housing 3| bya spring 89 on the shaft 81 acting-0n centrifugal weights 80. The disc86 s the blades 30 when the shaft 8 is rotating. Y

With such an arrangement it is possible to introduce liquid fuel intohollow rotor and to compress combustible vapors in the chamber 28 1Itshould be noted that the intermediate lining by the air admittedthrough the large blades 30 and heated by the compression in the secondstage, i. e., Venturi 35. The air, separated from the mercury, leavesthe condenser II by pipes 16 connected with a heating coil 11 supportedin the annular exhaust chamber 44 and are finally delivered by the pipe21 into the combustor as was explained above.

The gases from the combustor pass into the turbine at a temperature of1800-2000 F. or as high a temperature as the cooled blades and partswill stand. The ability to operate at such temperatures depends upon thematerials alone, but by cooling the parts subjected to suchtemperadelivering these vapors directly to the combustor 22. v

A starting motor 9| is provided for the rotor operated from a battery(not shown) which will 7 be charged by the motor when it is operated asa generator during rotationof the turbine shaft.

.The' shaft 81 can be connected by suitable gears82, 88 with a shaft 84of a propeller (not shown) or other mechanism.

58 between the shield metal and the refractory metal l4, 15 can be soselected as to take up the difference in expansion between the shieldmetal 7 and the refractory metal. a

It will .be understood that various features and principles of each ofthe embodiments of the. invention above described or referred to may beutilized or substituted in the other embodiments;

While the invention has been described in detall with respect to certainparticular preferred examples, it will be understood by those skilled inthe art after understanding the invention, that various changes andfurther modifications may be made without departing from the spirit andscope of the invention, and it is intended therefore in the appendedclaims to cover all such changes and modifications.

,pressor; means to set) rate the air from pors; and means to deliver theair into the comcompressors;

shaft rotatively supported in the end plates;-a' tubular rotor mountedon the shaft in the housseparated air by the exhaust gases; and means to1deliver the heated air into the combustion cham- 4. In a combustionturbine the combination of a tubular housing; aplurality of rows ofspaced stationary blades in the housing; a rear and a front end plateclosing the ends of the housing;

a a shaft rotatively supported in the end plates; a

ing; a plurality of rows of blades on the rotor; the

rear end plate having an intake opening and the front end plate havingan exhaust opening;-ave's-' sel in a communication withthe intakeopening and comprising a combustion chamber; means to rear end platehaving an intake opening and the admit a cooling medium into the rotor,the shaft being hollow at one end; tubular ducts extendingradially fromthe shaft to the rotor blades; means to admit airand a cooling liouidinto the space- 4 in the rotor through the hollow. portion of the shaft;a compressor for he combustion chamber operatively connected to theshaft; means to admit-heated vapors with the air from the rotor into thecompressor; means to admit heated va-- pors with the air from thevabustion chamber.

the rotor into the com- 2. In a combustion turbine the combination of atubular housing; 'a-plurality of rows of spaced stationary blades in thehousing; a rear and a front end plate closing the ends of the housing; ashaft rotatively supported inthe end plates: a tubular rotor mounted ontheshaft. in the housing; a plurality of rows of blades'on the rotor;the rear end plate having an intake opening and the front end platehaving an exhaust opening; a vessel in a communication with the intakeopening and comprising a combustion chamber; means to admit a coolingmedium into the rotor, the shaft being hollow at one end; tubular ductsextending radially from the shaft to the rotor blades, the rotor bladeshaving cavitiesopening into the space in the rotor; the ducts beingadapted to admit air into the rotor through the hollow portion of theshaft; a compressor'for the combustion chamber operatively connectedwith the shaft; means to admit heated vapors from the rotor into the andmeans to admit fresh air into the compressor for cooling and condensingthe vapors; means to separate. the heated air from the condensed vapors;and means to deliver the heated air into the combustion chamber.

turbine the combination of 3. Ina combustion a tubular housing;'aplurality of rows of spaced Y stationary blades in the housing; a rearand a front end plate closin the ends of the housing; a

shaft rotatively-supported in the end plates; a tubular rotor mounted onthe shaft in the housin a plurality of rows of blades on the rotor; therear end plate having an intake opening and the front endplate having anexhaust opening; a vessel in a communication with the intakeopening andcomprising a combustion chamber;

tubular rotor mounted on the shaft in the housing; a plurality of rowsof blades on the rotor; the

front end plate having an exhaust opening; a vesand comprising acombustion chamber; means to admit a coolingmedium into the'rotor, therotor blades having cavities opening into the space in the rotor; theducts being adapted to admit air.

' operatively connected with the shaft; means to admit heated vaporsfrom the rotor into the com: pressor; means to admit fresh air into thecompressor'for cooling and condensing the vapors; means to. control thetemperature of the condenser; means to separate the hot air in thecondenser from the condensed liquid; and means to deliver the separatedhot air into the combustion chamber.

5. In a combustion turbine the combination of a tubular housing; aplurality of rows of spaced stationary blades in the housing; a rear anda front end plate closing the ends of the housing; a shaft rotativelysupported in the end plates; a tubular rotor mounted on the shaft in thehousing; a plurality of rows of blades on the rotor; the rear end platehaving an intake opening and the front end plate having an exhaustopening; a vessel in a communication with the intake opening andcomprising acombustion chamber; means to admit a cooling medium into therotor, the shaft being hollow at one end; tubular ducts extendingradially from the shaft to the rotor blades; a Venturi restriction atone end of the shaft; a nozzle extending into the Venturi restriction;means to deliver a liquid through the nozzle and Verituri restrictioninto the hollow I shaft; and means .to admit outside air into theVenturi restriction. 1

6. In a combustion turbine the vcombination of a tubular housing; aplurality of rows of spaced vstationary blades in the housing; a rearand a front end plate closing the ends of the housing;

rotor; the rear end plate having an intake opening and-the front endplate having an exhaust opening; a vessel in, communication with theintake openingand comprising a combustion chamber; means to admit acooling medium into the rotor; the shaft being hollow at one end;tubular ducts extending radially'from the shaft to the means to admit acooling medium into the rotor, I

the shaft being hollow at one end; tubular ducts extending radially fromthe-shaft to'the rotor blades, the rotor blades havin cavities openinginto the space in the rotor; the ducts being adapted to admit air intothe rotor through thehollow portion of the shaft; a compressor for thecombustion chamber operatively connected with the rotorblades; aVenturi'restrlction at one end of.

the shaft; a nozzle" extending into the Venturi restriction; means todeliver a liquid through the nozzle and Venturi restriction into thehollow shaft; means to admit heated vapors from the I rotor into thecompressor; means to admit fresh air into the compressor for cooling andcondensing the vapors; means to separate the heated air i from thecondensed vapors; means to heat the shaft; means to admit'outside airinto the Ven-' turl restriction; and means responsive to-the pressure inthey nozzle to regulate the position of the nozzle in the Venturirestriction.

'h-In a'combustion turbine the combination of a tubular housing; aplurality of rows of spaced stationary blades in the housing; a rear anda front end plate closing the ends of the housing;

a shaft rotatively supported in the end plates;

sel in a communication with the intake opening I ing; a plurality ofrows of blades on the rotor; the

rear end plate having an intake opening and the' front end platehavingan exhaust opening; a vessel in a communication with theintakeopening and comprising a combustion chamber; means to admit a coolingmedium into the rotor; the shaft being hollow at one end; tubular ductsextending radially from the shaft to therotor blades; a Venturirestriction at one end of the shaft; a nozzle extending into the Venturirenozzle and'Venturi restriction-into the hollow tion; and curved bladesin the nozzle, the blades being curved in a direction for producingreaca tubular rotor mounted on the shaft in the housstationary blades inthe housing;-

a shaft rotatively supported in the end plates;

front end plate closing the ends of the housing;

" a tubular rotor mounted'on the shaft in the housstrlctionrmeans todeliver a liquid through the shaft; means to admit outside air into theVenturi restriction; turbine'blades in the Venturi restric tion forces,augmenting the rotory torque of the rotor..

8. In a combustion turbine the combination of a tubular housing; aplurality of rows of spaced stationary blades in the housing; arear anda front end plate closing the ends of the housing; a shaft rotativelysupported in the end plates; a tubular rotor mounted on the shaft in thehousing; a plurality of rows of blades on the rotor; the rear end platehaving an intake opening and the front end plate having an exhaustopening; a vessel in a communication with the intake opening andcomprising a combustion chamber; means to admit a cooling medium intothe rotor, the

shaft being hollow at one end; tubular ducts exinto the combustionchamber.

tending radially from the shaft to the rotor blades; means to admit avaporizable liquid into the rotor through the shaft and through theducts thereby obtaining vapors at a high pres-' mg; a plurality of rowsofblodes on the rotor; the rear'end plate having an intake opening andthe thefront end'plate having an exhaust'opening; a vessel in acommunication with the intake opening and comprising a combustionchamber; means to admit a cooling medium into the rotor, the shaft beinghollow at one end; tubular ducts extending radially from thef-shaft tothe rotor blades; means to admit a vaporizable liquid. fuel into therotor. and thereby obtaining vapors at a high, pressure; 'a centrifugalcompressor operated by the shaft; and means to admit the vapors SANFORDE. RICHESON. REFERENCES CITED The following references are of record inthe file of this patent:

/ UNITED STATES PATENTS Number Name Date 1,164,091 Herz Dec. 14, 19151,421,087 Johnson June 27, 1922 1,828,782 Morton Oct. 27, 1931 2,154,481Vorkauf Apr. 18, 1939 2,304,259 1 Karrer Dec. 8, 1942 and means to admitthe vapors into the" a rear and a

